扩压器

乘方和QUICK格式在非对称扩压器内流动计算的比较

Power-law and quick schemes in numerical study of nonsymmetry diffuser

二次喉道扩压器对COIL的影响实验

Experimental study on influence of secondary - throat diffuser on COIL

结果表明，采用求解N－S方程的方法计算高空台扩压器性能是一种有效的方法。

The results show that the method of soluting Navier Stokes equations is effective to predict the diffuser performance .

模型B则是一个空间S形扩压器，它的中心线在水平和垂直两个方向有相同的偏距。

Model A is an S-shaped diffuser with a horizontal offset only , and model B is space S-shaped with horizontal and vertical offsets .

离心压缩机无叶扩压器内部流场的PIV试验测量

PIV Measurement of Flow Field within Vaneless Diffuser of Centrifugal Compressor

离心叶轮机械有叶扩压器内部流动的PIV测量

PIV measurements of the unsteady flow in the vaned diffuser of a centrifugal fan

叶片扩压器内部非定常流动的PIV测量

PIV Measurement of Unsteady Flow within Blade Diffusor

有叶扩压器内部流场的PIV实验测量

PIV ( Particle Image Velocimetry ) Experimental Measurements of the Flow Field in a Bladed Diffuser

通过改变叶片数和出口安装角构造扩压器，进行CFD分析，建立样本数据。

Through changing vane number and exit installation angle to construct candidate diffusers which are analyzed by CFD , sample data is then setup .

采用基于同位网格的SIMPLE方法求解GAO-YONG不可压湍流方程组，对二维扩压器流动进行了数值模拟。

A two-dimensional incompressible diffuser flow was numerically simulated employing no staggered grid arrangement and incompressible SIMPLE method to solve GAO-YONG turbulence equations .

在小流量工况下，采用PDA技术对一旋转离心叶轮内部的速度场进行了测量与分析，叶轮出口带有无叶扩压器。

Phase doppler anemometer ( PDA ) technique was adopted to investigate the internal flow field within a centrifugal impeller under low flow rate operating condition .

优化后的透平末级与扩压器部分的CFD预测效率提高了2.8%，同时扩压器的长度缩短了30.1%。

After the optimization , efficiency of last stage and diffuser predicted by CFD code has increased by 2.8 % , and the length of diffuser was shortened by 30.1 % .

使用GAO-YONG湍流模型对扩压器流动的计算

The Calculation of Diffuser Flow Using GAO-YONG Turbulence Equations

离心叶轮出口与无叶扩压器内部流动特性的DPIV实验研究

Digital Particle Image Velocimetry ( DPIV ) investigation of the flow characteristics within the vaneless diffuser of a centrifugal blower

用PRO-E软件对进气弯管，带分流叶片的叶轮及有叶片扩压器进行了实体建模。

Using software PRO-E to build the model of the impeller 、 diffuser with blade 、 entering air elbow 、 volute .

应用隐式AF方法计算了为发动机进气道设计的典型扩压器内的复杂湍流流场。

Which is of great use for further application . A complicated turbulent flow field in a diffuser with typical geometric shape for aeroengine inlet design was calculated by the use of the implicit AF method .

采用粒子图像速度仪（PIV）测量了离心风机叶轮及扩压器的内部流场，并将绝对速度场换算成相对速度场，对其流动特性进行了讨论分析。

PIV is used to measure the flow field at impeller 's outlet and diffuser of centrifugal fan and the velocity field is recorded . The flow field characteristic after transferring the absolute velocity to relative is analysed .

建立了一种基于模糊理论的无叶扩压器优化模型，并采用人机交互的修改单纯形法（IMS）进行求解，模型同时考虑了扩压器的静压升和全压损失。

An optimization model based on fuzzy theory was set up and the corresponding IMS ( interactive modified simplex ) method was developed to solve it . Both static pressure recovery and total pressure loss are considered in the model .

通过对火箭发动机－超音速扩压器－蒸汽引射泵组合式高空模拟系统的理论分析和实验研究，提出了扩大GS－1高空模拟试车台试验能力的几项新方案。

In this paper , high altitude simulation test system composed of rocket engine , supersonic diffuser and vapour jet vacuum pump is analysed theoretically and studied experimentally . Several new methods used to extend test ability of GS-1 High Altitude Simulation Test Bed are proposed .

本文最后对带有扩压器的模型燃烧室进行了研究，结果表明射流孔面积与旋流器进口面积之比这一几何参数对RQL低污染燃烧的流量分配有十分重要的影响。

The results of investigation relating to diffuser in this thesis indicate that the ratio of jet holes area to the inlet area have affect on flow distribution of RQL combustor .

应用STAR-CD流动分析软件和PISO算法，采用滑移网格和多重旋转坐标系技术，全流场计算了旋转叶轮和叶片扩压器耦合的非定常流动。

The unsteady interaction between rotating impeller and vaned diffuser in a whole flow field is numerically investigated with STAR-CD , and PISO algorithmic , sliding mesh and multi-rotating coordinates are employed to solve the governing equations .

实验测得用保形通道式微型扩压器M0-C替代原型M0-A装配于发动机，可以使发动机的推力在最大转速下提高约11%，耗油率降低约9%。

The experimental data shows that the M0-A is replaced with the conformal passage diffuser M0-C , the thrust of the engine at the maximum speed can increase 11 % , the SFC can reduce by 9 % .

对MJ-M1扩压器进行了早期设计，结果表明MJ-M1的初步方案在压力系数大约0.55的情况下获得了高于0.93的总压恢复系数。

The early design of the diffuser MJ-M1 shows that it can get a higher total pressure recovery coefficient than 0.93 and the pressure coefficient is about 0.55 . Thirdly , the designed compressor is used in MJ-M1 micro turbine engine .

基于模糊理论的三维无叶扩压器多目标优化

The Multi-Criteria Optimization of 3D Vaneless Diffuser Based on Fuzzy Theory

亚声速圆锥扩压器内紊流可压缩流动的数值计算

Numerical calculation of subsonic compressible turbulent flow in a conical diffuser

离心式压气机无叶扩压器热力计算新方法

A New Thermodynamic Calculation Method of Vaneless Diffuser in Centrifugal Compressor

进口为均匀剪切流的二元亚音扩压器

Two-dimensional subsonic diffuser flow with uniform shear velocity profile at inlet

进样口温度，200℃；（2）楔形扩压器；

Inlet temperature : 200 ℃; ( 2 ) wedge-shaped diffuser ;

有叶扩压器在改进离心压缩机性能中的应用

Application of Vaned Diffuser in Improving the Performance of Centrifugal Compressor

在激光器背压升高时，二次喉道扩压器的稳定性更强。

The secondary-throat diffuser is propitious to COIL at high back-pressure .